Turbine gas-engine.



J. J. SMIDDY.

TURBINE GAS ENGINE.

APPLICATION FILED OUT. 29, 1910.

1,132,742. Patented Mar. 23, 1915.

2 SHEETS-SHEET 1.

@ Jmmel 51221362 1 MM m ATTORNEY J. J. SMIDDY.

TURBINE GAS ENGINE.

APPLICATION FILED OUT. 29, 1910.

ATTORNEY 2 SHEETSSHEET 2.

INVENTOR J Sm/zdd 1 Patented Mar. 23, 1915.

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JEROME J. 'SMIDDY, OF HONOLULU, TERRITORY OF HAWAII.

. TURBINE GAS-ENGIN E.

Specification of Letters Patent.

Patented Mar. 23, 1915.

Application filed October 29, 1910. Serial No. 589,757.

To all whom it may concern:

Be it known that I, JEROME J. SMIDDY, a citizen of the United States, residing at Honolulu, in the District of Oahu, on the Island of Hawaii, have invented a certain new and useful Improvement in Turbine Gas-Engines, of which the following is a specification.

My invention relates to a new and useful improvement in turbine gas engines, and has for its object to provide a device of this character in which a rotor is used having teeth, projections or buckets formed upon the periphery thereof, against which the exploded gas operates, and in order that the gas may have some object against which it may expand, I provide a portion of the internal face of the casing with teeth, projections or buckets similar to those upon the rotor.

Another object of the invention is to construct a turbine gas engine with mechanically operated valves, each connected with the shaft on which the rotor is mounted, so that they may be timed to operate correctly.

Another object of the invention is to pro vide the supply pipe with a pump casing, the. gas to enter the explosion chamber under high pressure.

With these ends in view, this invention consists in the details of construction and combination of elements hereinafter set forth and then specifically designated by the claims.

In order that those skilled in the art to which this invention appertains may understand how to make and use the same, I will describe its construction in detail, referring by letter to the accompanying drawing forming a part of this specification, in which Figure 1 is a vertical sectional view of a turbine gas engine made in accordance with my improvement. Fig. 2, a side elevation thereof, showing the valve operating mechanism. Fig 3, a side elevation of the opposite side of-"the engine showing the supply pipes and pump, and Fig. 4, an end view thereof.

In carrying out my invention as here embodied, A represents the base, with which is formed the casing B, having passageways C for water in order that the engine may be kept at a low temperature. This casing is formed first to produce a rotor chamber D, the walls of which are notched or toothed as at E. Leading to this chamber are two inlet ports F, leading from the explosion chambers G, one being formed at each end of the casing. In each of the inlet ports F is mounted a valve H having a. passageway I and having attached thereto a rocker arm J for operating the valve, as will be hereinafter described.

K represents an intake passage having a threaded opening L for the reception of the supply pipe M. This intake enters the casing beneath the explosion chamber, following the line of the explosion chamber until it reaches the end thereof, at which point is formed a valve opening N, which is normally closed by the valve 0 mounted upon the lnner end of the valve stem P, which passes through the casing and is pivoted to the swinging lever Q, said lever being pivoted at Q to the bracket Q the opposite end of said lever being fastened to one end-of the rod B, said rod being attached to the rocker arm J. About the valve stem P is placed a coil spring S, one end thereof resting against the casing, the opposite end against the lever Q for holding the valve when closed securely against the walls of the casing surrounding the valve opening N. Leading to the top of the explosion chamber G is a threaded opening T, in which is mounted aspark plug U, having connection with a source of electricity in the ordinary manner for exploding the charge within the chamer G. Leading from the top and bottom of the casing are the exhaust ports V, through which pass the burnt gases, and to these may be connected pipes for carrying the exhaust to any point desired.

W represents a shaft journaled in the heads or sides of the casing, and on these are mounted the eccentrics X having attached thereto the rods Y, which are also fastened to the rocker arms J for operating the-Corliss valves H and the valves 0. On this shaft within the casing is mounted the rotor Z, having notches, teeth, projections or buckets A formed upon its periphery adapted to receive the gases fro-m the explosion chamber, said gases as they expand forcing the rotor to revolve. Upon the shaft W is mounted another cam B to which is attached the piston rod C of the pump D, said pump having connection with the carbureter E and the supply pipes M.

In practice as the rotor revolves the shaft W will be caused to do likewise, which through the medium of the cam B will cause the pump D to draw the gas from the carburetor E and forceit under pressure through the supply pipes M to the intake ports K, from which point the gas will enter the explosion chamber G as the valve opening N is opened by the valve 0, which is operated through the medium of the pivoted lever Q, the rods R and Y and the cams X, which are mounted upon the shaft W. At a predetermined time this mixture is exploded, the "alve H opened, allowing the exploded gas to pass through the inlet port F into the rotor chamber D, at which point it will expand against the teeth or buckets of said rotor, and the teeth of the casing continuing to expand and work upon the rotor until it reaches the exhaust V, from which point it will pass to the atmosphere;

Of course I- do not wish to be limited to the exact details of construction here shown as these may be varied within the limits of the appended claims without departing from the spirit of my invention.

Having thus fully described my invention, what I claim as new and useful, is-

1. In a turbine gas engine, the combination of a casing having projections formed at each side thereof to produce combustion chambers, each of said combustion chambers being connected by a port to the interior of the casing, said ports running in opposite directions for guiding the motive fluid, a series of serrations formed on the interior of the casing above one of the said ports, a similar series of serrations located below the opposite port, rotary valves, one located in each port for intermittingly admitting the motive fluid, first to one side of the casing and then to the other, a rotary member journaled in the casing, and providedwith peripheral serrations projecting at an angle from said member, mechanism operated by the revolv-.

ing of the rotary member for operating the rotary valves in unison, valves for admitting the explosive mixture to the combustion chambers, and means for operating the last named valves in unison with the rotary valves.

2. In a turbine gas engine the combination of a casing provided with a rotor chamber and a pair of oppositely disposed combustion chambers connected with the rotor chamber by suitable ports, one of said ports leading upwardly and the other downwardly, valves situated Within said ports and outlet ports leading from the rotor chamber, valves for controlling admission .of an explosive mixture to the combustion chamber, means for operating all of the valves in unison, serrations formed on the interior of the casing, one set above one of the ports and the other set below the other port, a rotor revolubly mounted in the rotor chamber and peripheral serrations carried by the rotor and projecting at an angle therefrom, as shown and for the purpose described.

In testimony whereof, I have hereunto affixed my signature in the presence of two subscribing witnesses.

JEROME J. SMIDDYQ Witnesses FRANK HUSTACE, H. CLARK. 

